Extensible airplane wings



Apri14, 1967 Filed sept. 27, 1965 J. B. GUIN EXTENSIBLE AIRPLANE WINGS 2 Sheets-Sheet 1 IN VENTOR.

April 4, 1967 J. B.- GUIN EXTENSIBLE AIRPLANE WINGS 2 Sheets-Sheet 2 Filed Sept. 27, 1965 FIGA INVENTOR.

United States Patent Gtlice 3,312,428 Patented Apr. -4, 1,967

3,312,428 EXTENSIBLE AIRPLANE WINGS `oel B. Guin, 148 E. 48th St., New York, N.Y. 10017 Filed Sept. 27, 1965, Ser. No. 490,449

3 Claims. (Cl. 244-43) This invention relates to extensible airplane Wings that permit the using plane to take oil", ily, glide, maneuver and land over a much. broader range of slow speeds than is possible with rigid wings, thus gaining such advantages Much shorter runways or jungle strips can be used for both military and commercial planes;

The plane can remain airborne for a much longer time and glide much farther, to conserve dwindling fuel, or in emergencies such as Vloss of power, loss of part of a wing, other damage to the plane, injured crew members and/ or pilot, etc. (a Pan Am pilot who coaxed his 707 in after losing 1/3 of a wing was a hero: Vwith these wings a lot of pilots would -be heroes instead of dead, and a lot of passengers would be grateful instead of dead);

If an airport is fogged in, the traffc pattern is too hig-h in ratio to his fuel supply or the soup is too thick, or if the jungle airstrip shows signs of enemy possession or proximity, the pilots range of choices will be multiplied many times with these wings (his face -gets red if the only way to go is down);

Taking off, flying and landing at slow speeds will save fuel, money and lives (any pilot of a commercial, private or military plane who has lived through a forced landing on land or sea, either at night or in the day, does not have to be told how comforting it would be to know he has the ability, when it arrives, to swoosh in at 20 to 60 mph. instead lof 80 to 200 m.p.h.). y

These advantages and objects will be clear, and others will appear when the inclosed description is read in connection with the accompanying drawings in which FIG. l is a side view of an airplane with folding wings, the wings being in folded position;

FIG. 2 is an enlarged vertical section along line 2--2 in FIG. 1 showing the folding wings in folded position;

FIG. 2A corresponds to FIG. 2 with wings extended;

FIG. 3 is a top view of airplane in FIG. 1 with folding wings extended;

FIG. 4 is a vertical section through the hinge connecting the two folding wing parts, here shown collapsed;

FIG. 4A shows the hinge of FIG. 4 with wing parts extended;

FIG. 5 is a side view of an airplane with a modified version of folding wings, called para-wings, which extend thru a slit in the side of the plane;

FIG. 6 is an enlarged vertical section along line 6-6 in FIG. 5 showing the flexible para-wings folded within theplane;

FIG. 7 is a top view of the plane in FIG. 5 with the para-wings extended.

Turning now to the drawings, FIG. 1 shows airplane 1 having main wing 2, crew compartment 3, stabilizer 4 and rudder 5. Connected to the plane is a folding wing consisting of parts 7 and 8, the latter being covered by sliding door 6.

FIG. 2 is a vertical section along line 2-2 in FIG. 1 showing left and right parts 7 and 8, 7A and 8A respectively, which are joined at the top by hinges 1()` and 10A and are positioned within wing compartments 11 and 11A respectively. The inner folding wing parts are connected at the bottom to hinges 12 and 12A, and to compressed air units 13 and 13A respectively, the latter standing on oor 14. Upper structure 9 is attached to horizontal plate 15 to form the ceiling, below which are the inner walls 18 and 18A of the wing compartments.

FIG. 2A shows the folding wings of FIG. 2 extended,

having turned on hinges 12 and 12A through the action of compressed air units 13 and 13A respectively, in forcing out curved devices 19 and 19A which are attached to win-g parts 8 and 8A respectively, the curved devices normally being drawn into units 79 and 13A (they could be extended equally well be electrically activated devices).

FIG. 3 is a top view of the plane in FIG. 1 with the folding wing parts 7 and 8, 7A and 8A, extended. Also shown are wing compartments 11 and 11A, and sliding doors 6 and 6A.

FIG. 4 is a vertical section through the hinge connecting the two folding wing parts 7A and 8A with covering plates 21 and 20 respectively. Connected to structure 20 having indentation 29 is a fastening part 27 to which is fastened rope holder 28. Connected to plate structure 21 having extension 30 (designed to t into indentation 29), is fastening part 27A. A rope 26 reaches throu-gh wing part 7A, is lead around guide 23 with groove 24, and is fastened to rope holder 28. Both Wing parts turn around hinge 31.

FIG. 4A shows the wing parts 8A and 7A of FIG. 4 rotated deg. around hinge 31 to the left and right respectively. Rope 26 has been pulled in t-he direction of arrow 34. The two fastening parts 27 and 27A have joined, clamping the two win-g parts together mechanically. i

FIGURES 5, 6 and 7 show a modified version of folded wings, calle-d para-wings, FIG. 5 being a side View, FIG. 6 a vertical section along line 6-6 in FIG. 5, and

FIG. 7 being a top view. Para-wings 37 and 37A are auxiliary wings which can be drawn t-hrough slit 35 by telescoping beams 40 and 40A which in turn are extended through slits 36 and 36A respectively. Para-wings 37 and 37A have outer beams 3S and 38A and supporting beams 39 and 39A respectively. Outer beams 38 and 38A and slits35 and 35A respectively should be designed so that the former will fit snugly into the latter and leave a streamlined outer surface on the fuselage.

In FIG. 6 the folded para-wings 37 and 37A are wound on conical drums 44 and 44A respectively which in turn are held by beams 43 and 43A respectively; fastened to these are compressed air units 46 and 46A respectively which are connected lby hinges 47 and 47A to extension beams 40 and 40A respectively, which have telescoping sections 41 and 41A as shown in FIG. 7. These telescoping extension beams 40 and 40A can be extended sidewise through slits 36 and 36A respectively, and are fastened to the para-wings at points 42 and 42A respectively, which glide around rollers 45 and 45A respectively when extended.

In FIG. 7 the para-wings are extended, the outer edges being drawn taut by outer beams 38 and 38A and supporting beams 39 and 39A respectively. Extensible and retractable telescoping beams 40 and 40A (the points between sections being shown along with the sections 41 and 41A) with the outer ends attached at points 42 and 42A to outer beams 38 and 38A respectively, are the principal means for stabilizing and strengthening the parawings.

I claim:

1. Auxiliary para-wings for airplanes to improve their safety and economy by enabling them to take olf, fly, glide, maneuver, and land over a broad range of slow speeds, comprising:

two drum beams each mounted within and attached to the surface of the fuselage of an airplane near one of the walls thereof;

two drums each designed to have one para-wing wound upon it and rotatably mounted upon one of said drum beams;

two series of rollers, each series designed to have one of the para-wings roll over it as it is extended and retracted, and rotatably mounted upon one of the inner walls of the fuselage; two horizontal wing slits, each cut through one wall of said fuselage for the passing of the para-wing through it;

, two vertical beam slits for passage of telesco-png beams,

each cut through the wall of said fuselage near the aft end of one kof said horizontal wing slits;

two telescoping beams, each extensible and retractable,

each made of several telescoping sections, and rotatab-ly mounted upon a hinged shaft within a mechanical activation unit located near the bottom of said vertical beam slits through which it swings outward as it is extended, and being fastened by its outer end to t-he aft end of one of two outer beams;

two mechanical activation units, electrically powered, each mounted upon the inner surface of said fuselage near the bottom of one of said vertical beams, and having attached to a hinged shaft within, the lower end of one of said telescoping beams, the unit being designed to extend and retract said telescoping supportbeam through said vertical beam slit;

two triangular para-wings, eac-h attached to an outer beam which is movahly attached at the triangles apex to the lside of said fuselage near the front end of said horizontal wing slit, having support beams running through it from its apex to its base, having its base edge wound upon one of said drums when not extended, and having its outer beam attached to the outer section of said telescoping beam;

all components working together so that when said mechanical activation unit (one on each side) is alerted, it begins to extend said telescoping beam and through it said outer beam attached to the outer end thereof, thus unwinding said para-wing till it 1s 'fully extended and locked in position; the reverse procedure being used to retract the para-wingiand rewind it on the drum. 2. T he substance of claim 1, said mechanical activation unit being powered with compressed air.

3. The substance of claim 1, said mechanical activation unit being powered by an electric motor.

Y References Cited by the Examiner vUNITED STATES PATENTS 1,792,764 2/ 1931 Salisbury et al. 244-43 2,193,029 3/1940 Juul 244-139 2,343,645 3/1944 Dickenson et al. 2,376,636 5/ 1945 Thompson 244-43 2,681,773 6/1954 Rethorst 244-49 X 3,065,938 11/ 1962 Clakins 244-49 X 3,163,382 12/ 1964 Messerschmitt 244-102 3,197,158 7/1965 Rogallo 244-49 FOREIGN PATENTS 290,809 11/ 1931 Italy. 507,423 12/ 1954 Italy.

MILTON BUCHLER, Primary Examiner.

B. BELKIN, Assistant Examiner. 

1. AUXILIARY PARA-WINGS FOR AIRPLANES TO IMPROVE THEIR SAFETY AND ECONOMY BY ENABLING THEM TO TAKE OFF, FLY, GLIDE, MANEUVER, AND LAND OVER A BROAD RANGE OF SLOW SPEEDS, COMPRISING: TWO DRUM BEAMS EACH MOUNTED WITHIN AND ATTACHED TO THE SURFACE OF THE FUSELAGE OF AN AIRPLANE NEAR ONE OF THE WALLS THEREOF; TWO DRUMS EACH DESIGNED TO HAVE ONE PARA-WING WOUND UPON IT AND ROTATABLY MOUNTED UPON ONE OF SAID DRUM BEAMS; TWO SERIES OF ROLLERS, EACH SERIES DESIGNED TO HAVE ONE OF THE PARA-WINGS ROLL OVER IT AS IT IS EXTENDED AND RETRACTED, AND ROTATABLY MOUNTED UPON ONE OF THE INNER WALLS OF THE FUSELAGE; TWO HORIZONTAL WING SLITS, EACH CUT THROUGH ONE WALL OF SAID FUSELAGE FOR THE PASSING OF THE PARA-WING THROUGH IT; TWO VERTICAL BEAM SLITS FOR PASSAGE OF TELESCOPING BEAMS, EACH CUT THROUGH THE WALL OF SAID FUSELAGE NEAR THE AFT END OF ONE OF SAID HORIZONTAL WING SLITS; TWO TELESCOPING BEAMS, EACH EXTENSIBLE AND RETRACTABLE, EACH MADE OF SEVERAL TELESCOPING SECTIONS, AND ROTATABLY MOUNTED UPON A HINGED SHAFT WITHIN A MECHANICAL ACTIVATION UNIT LOCATED NEAR THE BOTTOM OF SAID VERTICAL BEAM SLITS THROUGH WHICH IT SWINGS OUTWARD AS IT IS EXTENDED, AND BEING FASTENED BY ITS OUTER END TO THE AFT END OF ONE OF TWO OUTER BEAMS; TWO MECHANICAL ACTIVATION UNITS, ELECTRICALLY POWERED, EACH MOUNTED UPON THE INNER SURFACE OF SAID FUSELAGE NEAR THE BOTTOM OF ONE OF SAID VERTICAL BEAMS, AND HAVING ATTACHED TO A HINGED SHAFT WITHIN, THE LOWER END OF ONE OF SAID TELESCOPING BEAMS, THE UNIT BEING DESIGNED TO EXTEND AND RETRACT SAID TELESCOPING SUPPORT BEAM THROUGH SAID VERTICAL BEAM SLIT; TWO TRIANGULAR PARA-WINGS, EACH ATTACHED TO AN OUTER BEAM WHICH IS MOVABLY ATTACHED AT THE TRIANGLE''S APEX TO THE SIDE OF SAID FUSELAGE NEAR THE FRONT END OF SAID HORIZONTAL WING SLIT, HAVING SUPPORT BEAMS RUNNING THROUGH IT FROM ITS APEX TO ITS BASE, HAVING ITS BASE EDGE WOUND UPON ONE OF SAID DRUMS WHEN NOT EXTENDED, AND HAVING ITS OUTER BEAM ATTACHED TO THE OUTER SECTION OF SAID TELESCOPING BEAM; ALL COMPONENTS WORKING TOGETHER SO THAT WHEN SAID MECHANICAL ACTIVATION UNIT (ONE ON EACH SIDE) IS ALERTED, IT BEGINS TO EXTEND SAID TELESCOPING BEAM AND THROUGH IT SAID OUTER BEAM ATTACHED TO THE OUTER END THEREOF, THUS UNWINDING SAID PARA-WING TILL IT IS FULLY EXTENDED AND LOCKED IN POSITION; THE REVERSE PROCEDURE BEING USED TO RETRACT THE PARA-WING AND REWIND IT ON THE DRUM. 